Results
2012-08-16: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 60 airplanes. This AD was prompted by two incidents of swapped fire extinguishing wires. This AD requires inspecting the electrical leads routed to the fire extinguishing containers for proper identification and missing labels, and to ensure the electrical leads are connected to the correct squibs; and corrective actions if necessary. We are issuing this AD to prevent the extinguishing agent of the fire extinguishing container from being delivered to the wrong engine in the event of an engine fire, and a consequent uncontrolled fire.
74-14-05: 74-14-05 BEECH: Amendment 39-1892. Applies to those Model B-19 (Serial Numbers MB-481 through MB-634 and MB-649) and those Model C-23 (Serial Numbers M-1285 through M-1493, except M-1437 and M-1491) airplanes which were originally approved in the Acrobatic Category and intentional spins in the Utility and Acrobatic Categories. Compliance: Required as indicated, unless already accomplished. To prevent inflight situations in which prompt spin recovery may not be assured, accomplish the following: A) Effective immediately intentional spins in the Utility and Acrobatic Categories are prohibited. B) Within the next 20 hours' time in service or ten (10) calendar days, whichever comes first, after the effective date of this AD, unless already accomplished per AD 73-14-8, Amendment 39-1683, remove all placards pertaining to intentional spins and acrobatic flight and install in place thereof a placard to be conspicuously located on the instrument panel which reads as follows: "THIS AIRPLANE MUST BE OPERATED AS A NORMAL OR UTILITY CATEGORY AIRPLANE. INTENTIONAL SPINS ARE PROHIBITED. NO ACROBATIC MANEUVERS APPROVED EXCEPT: CHANDELLES, LAZY EIGHTS, STEEP TURNS, AND STALLS (EXCEPT WHIP STALLS)." C) To reinstate the acrobatic category for those airplanes originally approved in the Acrobatic Category and intentional spins in Utility and Acrobatic Categories, install Beech spin improvement Kit No. 23-4007-1 S in accordance with instructions contained therein, or any equivalent method approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Central Region. Upon installation of said Kit, requirements of Paragraphs A) and B) of this AD are no longer applicable. This AD supersedes AD 73-14-8, Amendment 39-1683. This amendment becomes effective July 10, 1974.
65-22-04: 65-22-04 VICKERS: Amdt. 39-141 Part 39 Federal Register September 28, 1965. Applies to Viscount Models 744, 745D and 810 Series Airplanes. Compliance required as indicated. To prevent failure of the main landing gear retraction jack attachment bolt, accomplish the following: (a) For Models 744 and 745D Series airplanes with attachment bolts, P/N's 70150-495, 74450-103, 72450-275, or 74550-51, and Model 810 Series airplanes with attachment bolts, P/N's 74450-103 or 74550-51, comply with (c) within the next 350 hours' time in service after the effective date of this AD, unless already accomplished. (b) For Models 744 and 745D Series airplanes with attachment bolts, P/N's 72450-291 or 74550-67, and Model 810 Series airplanes with attachment bolts, P/N's 74550-67 comply with (c) within the next 1,300 hours' time in service after the effective date of this AD unless already accomplished. (c) Remove and inspect attachment bolts, P/N's 70150-495, 72450-275, 74450-103,74550-51, 72450-291, or 74550-67, in accordance with B.A.C. Ltd. PTL No. 259 (744 and 745D) and PTL No. 123 (810) or FAA-approved equivalent. Replace bolts having helical markings or surface cracks in accordance with PTL No. 259 or No. 123 as applicable. If a bolt is found to be completely broken through, inspect the associated trunnion or eye end for cracks. Replace any cracked trunnions or eye ends before further flight with a part of the same part number or an FAA-approved equivalent. This directive effective September 25, 1965.
2012-08-04: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of the air driven generator (ADG) failing to power essential buses during functional tests, due to the low threshold setting of the circuit protection on the ADG's generator control unit (GCU) preventing the ADG from supplying power to the essential buses. This AD requires installing a new or serviceable ADG GCU. We are issuing this AD to prevent loss of power from the ADG to the essential buses which, in the event of an emergency, could prevent continued safe flight.
98-21-27: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes that are equipped with the "corporate commuter cabin layout." This layout is a Pilatus designation only and the affected airplanes are not certificated for commuter operation. This AD requires modifying the passenger seats and seat rail covers. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent passenger injuries because the passenger seat configuration has been found to not fully meet current head injury criteria regulations.
2012-08-05: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), CL-600-2D24 (Regional Jet Series 900), and CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of the air driven generator (ADG) failing to power essential buses during functional tests, due to the low threshold setting of the circuit protection on the ADG's generator control unit (GCU) preventing the ADG from supplying power to the essential buses. This AD requires installing a new [[Page 24365]] or serviceable ADG GCU. We are issuing this AD to prevent loss of power from the ADG to the essential buses which, in the event of an emergency, could prevent continued safe flight.
2011-18-52: We are publishing a new airworthiness directive (AD) for certain Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters that requires establishing a revised life limit for each tail rotor (T/R) blade and updating the helicopter's historical records, repetitively inspecting T/R blades for a crack, and replacing certain T/R blades. This AD is prompted by a fatal accident involving an Agusta Model AW139 helicopter, which may have been caused by cracks in a T/R blade. These actions are intended to detect and prevent a crack in a T/R blade, which could lead to failure of a T/R blade and subsequent loss of control of the helicopter.
98-21-26: This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Models M20J, M20K, M20M, and M20R airplanes. This AD requires grinding the surface of the main landing gear (MLG) leg bracket, inspecting this area for cracks, and replacing any cracked MLG leg bracket. This AD is the result of the manufacturing of several of the MLG leg brackets using laser pattern cutting. The brackets, when manufactured using this process, develop minor cracks at the bends, which could propagate over time. The actions specified by this AD are intended to prevent failure of the MLG side brace bolt caused by cracking of the MLG leg bracket, which could result in MLG collapse with consequent loss of control of the airplane during taxi, takeoff, or landing operations.
2012-03-04: We are superseding an existing airworthiness directive (AD) for certain Airbus Model A310 series airplanes. That AD currently requires, for certain airplanes, modifying the wire routing and installing additional protective sleeves. This new AD adds, for certain airplanes, modifying wire routings and installing a modified bracket. This AD was prompted by analyses of the wire routing showing that the route of the fuel electrical circuit in the right-hand wing must be modified in order to ensure better segregation between fuel quantity indication wires and the 115-volt alternating current wires. We are issuing this AD to prevent short circuits leading to arcing, and possible fuel tank explosion.
54-12-02: 54-12-02 MCCAULEY: Applies to All McCauley Propellers Having 41D5926 Hub With SS-135-6 Blades and D-1093 Hub With SS-135-6M or SS-138-6 Blades. Compliance required as indicated. On the basis of satisfactory vibration stress surveys conducted on the 102-inch diameter configuration, these propellers were approved vibration wise for installation on the Continental W-670-6A and W-670-6N and Lycoming R680 engines. When installed on the Continental engine, the propeller must be indexed in the 0 degree position (blades in line with the crankthrow) and operation is to be restricted between 1,500 and 1,650 r.p.m. Additional approval were given for the installation of propellers in reduced diameters at a time when the effects on the vibratory stresses resulting from such a reduction were not generally appreciated. Accordingly, some installations were made where the propeller diameter was reduced, as in the Fairchild M-62C. Service experience with this installation and a more thorough knowledge of the vibration problems indicate that diameters below the normal 2 percent reduction that is usually permissible on the basis of a stress survey have resulted in serious failures. Accordingly, to preclude additional propeller failures, the following should be performed. Compliance required prior to July 1, 1954. (a) To preclude failures due to vibratory conditions, remove from service all of these propellers in diameters outside the 102- to 100-inch limits. (b) To preclude fatigue failures due to corrosion or galling in the blade shank region and/or hub, disassemble propellers maintained in service (diameters 102 to 100 inches) and magnetically inspect hub and blades at intervals not exceeding 100 hours. The propeller blade and hub surface must be kept free from corrosion at all times. If 100 hours operating time has not been accumulated since an inspection was conducted on the propeller as provided in AD 47-43-09, it will be satisfactory to operate until 100 hours have been accumulated. This supersedes AD 47-43-09.
98-08-25 R1: This amendment revises Airworthiness Directive (AD) 98-08-25, which currently requires replacing the nose landing gear (NLG) drag link bolt with an approved heat-treated bolt that has the manufacturer's serial number, manufacture date, and the last three digits of the drawing number (055) on the bolt head on certain Twin Commander Aircraft Corporation (Twin Commander) 500, 680, 690, and 695 series airplanes; and changing the bolt part number (P/N) to be installed on Models 690D and 695A from P/N ED10055 to P/N 750076-1. The FAA inadvertently transposed the serial numbers of the 4 affected Model 695A airplanes. This AD retains the same actions of AD 98-08-25, and corrects the serial numbers of these 4 airplanes. Three of the four airplanes are not on the U.S. Register and the other one is already in compliance with the actions of AD 98-08-25. The actions specified in this AD are intended to continue to prevent the NLG from collapsing due to failure of a drag link bolt, which could result in loss of control of the airplane during landing operations.
2012-07-05: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.27 Mark 050 airplanes. This proposed AD would require performing a low frequency eddy current inspection for cracks of the lap joint of the rear fuselage, and repair if necessary. This AD was prompted by reports of cracking in the fuselage lap joint. We are issuing this AD to detect and correct exponential crack growth, which could lead to failure of the lap joint over a certain length and consequent in-flight decompression of the airplane.
98-21-05: This amendment adopts a new airworthiness directive (AD), applicable to all SD3-30, SD3-60, SD3-60 SHERPA, and SD3 SHERPA series airplanes, that requires repetitive visual inspections of the flap levers and bracket assembly of the inner flap sub-assembly of the left and right wings to detect certain discrepancies; and corrective actions, if necessary. This amendment is prompted by mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct failure of the levers and bracket assembly, which could result in uncommanded retraction of the inner flap assembly and consequent reduced controllability of the airplane.
2012-06-09: We are adopting a new airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G airplanes. This AD was prompted by a report of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their design service objective. This AD requires revising the maintenance inspection program to include inspections that will give no less than the required damage tolerance analysis for each principal structural element (PSE), doing repetitive inspections to detect cracks of all PSEs, and repairing cracked structure. We are issuing this AD to maintain the continued structural integrity of the fleet.
74-09-03: 74-09-03 AVCO LYCOMING: Amendment 39-1823. Applies to all Avco Lycoming T5309C, T5311A and T5311B turboshaft engines. Compliance required, unless already accomplished, prior to the accumulation of 100 hours in service after the effective date of this AD. To prevent possible compressor disc or impeller assembly failures leading to partial or complete loss of engine power, remove and replace the second, third, fourth, and fifth stage compressor rotor discs and centrifugal impeller assemblies in accordance with the table below. COMPONENT - 2nd Stage Compressor Rotor Disc; REMOVE P/N - 1-100-239-01; INSTALL P/N - 1- 100-239-04 or later FAA approved P/N COMPONENT - 3rd Stage Compressor Rotor Disc; REMOVE P/N - 1-100-242-01 or 1-100-242-06; INSTALL P/N - 1-100-242-09 or later FAA approved P/N COMPONENT- 4th Stage Compressor Rotor Disc; REMOVE P/N - 1-100-244-01 or 1-100-244-02; or 1-100-244-04 or 1-100-244-06; INSTALL P/N - 1-100-244-08 or later FAA approved P/N COMPONENT- 5th Stage Compressor Rotor Disc; REMOVE P/N - 1-100-417-01 or 1-100-417-02; INSTALL P/N - 1-100-417-05 or later FAA approved P/N COMPONENT - Centrifugal Impeller Assembly; REMOVE P/N - 1-100-440-04 or 1-100-440-07; INSTALL P/N - 1-100-440-07; Rev. B or later FAA approved P/N Upon submission of substantiating data through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance time. NOTE: (Avco Lycoming Service Bulletin Number 0033 pertains to this subject.) This amendment becomes effective May 2, 1974.
2012-06-24: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD was prompted by the discovery of tail rotor blade assemblies (blades) manufactured with mislocated aluminum wire mesh, leaving portions of the graphite torque tube (spar) region unprotected from a lightning strike. The actions are intended to detect mislocated blade wire mesh and to prevent spar delamination, loss of the blade tip cap during a lightning strike, blade imbalance, loss of a blade, and subsequent loss of control of the helicopter.
2012-06-10: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-300, A340-500, and A340-600 series airplanes. This AD requires a detailed inspection for cracked and missing nuts, and replacement of cracked or missing nuts with new nuts having the same part number. This AD was prompted by reports of cracked nuts detected during production. We are issuing this AD to detect and correct cracked or missing nuts, and replace all affected nuts in multiple locations (including fuel tank areas) that could result in reduced structural integrity of the airplane.
2012-06-23: We are superseding an existing airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211-Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211- Trent 892B-17, and RB211-Trent 895-17 turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections (UIs) of certain low-pressure (LP) compressor blades identified by serial number (S/N). This AD requires the same actions but expands the population of blades. This AD was prompted by RR concluding that additional blades affected must be inspected. We are issuing this AD to prevent LP compressor blades from failing due to blade root cracks, which could lead to uncontained engine failure and damage to the airplane.
59-12-03: 59-12-03 VICKERS: Applies to All Viscount 745D and 810 Series Aircraft. Compliance required by October 31, 1959. Two cases have occurred of the Graviner fire extinguisher cartridge types A216 and A217 failing to operate at altitudes exceeding 20,000 feet. The failures were due to a combination of altitude and temperature affecting the gunpowder charge. To preclude such failures the Graviner Manufacturing Company has issued Modification AU 393 introducing improved firing units type A716 (replacing type A216) and type A717 (replacing A217). The new units have a modified bridge wire arrangement and may be identified by a blue plastic band around the neck of the cartridge. The British Air Registration Board considers the embodiment of this modification mandatory. (Graviner Manufacturing Company Modification No. AU 393 and Vickers-Armstrongs PTL205 and Modification D.2926 (700 Series) and PTL 73 and Modification FG.1695 (800/810 Series) covers this subject.)
2012-07-01: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 helicopters with certain tail rotor blades (blades) installed. This AD requires, before further flight, removing and replacing each affected blade with an airworthy blade. This AD is prompted by incidents where a blade tip weight separated from a blade in flight on other model helicopters with common part-numbered blades. It has been determined that this unsafe condition may also exist on the specified Agusta model helicopters. The actions specified in this AD are intended to prevent loss of the blade tip weight, loss of a blade, and subsequent loss of control of the helicopter.
74-10-04: 74-10-04 PRATT & WHITNEY: Amendment 39-1831. Applies to all Pratt & Whitney Model JT9D-3A and JT9D-7 turbofan engines. Compliance required not later than February 1, 1975. 1. To prevent the possibility of internal main gearbox fires in the event of an internal gearbox failure, rework the main gearbox in accordance with Pratt & Whitney Service Bulletin No. 4043, dated February 5, 1973, or later Federal Aviation Administration approved revisions. 2. To prevent leakage of oil around carbon face seals, replace present seal assemblies with the redesigned carbon face seal assemblies per Pratt & Whitney Service Bulletin No. 3902, dated August 8, 1972, or later Federal Aviation Administration approved revisions or Federal Aviation Administration approved equivalent. 3. Equivalent methods of compliance to the requirements of paragraph 2 above must be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region. Themanufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Chief Engineer, Pratt and Whitney Aircraft, Division of United Aircraft Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at the Office of the Regional Counsel, New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803 and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D. C., and at the New England Regional Office in Burlington, Massachusetts. This amendment becomes effective May 14, 1974.
98-20-35: This amendment supersedes an existing airworthiness directive (AD), applicable to all IAI, Ltd., Model 1121, 1121A, 1121B, 1123, 1124, and 1124A series airplanes, that currently requires repetitive inspections of the trim actuator of the horizontal stabilizer to verify jackscrew integrity and to detect excessive wear of the tie rod, and replacement of the actuator or tie rod, if necessary. That AD also provides for optional terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the trim actuator of the horizontal stabilizer due to failure of the jackscrews, which could result in reduced controllability of the airplane. The incorporation by reference of certain publications was approved previously by the Director of the Federal Register as of April 10, 1998 (63 FR 11106, March 6, 1998).
76-02-06: 76-02-06 BELL: Amendment 39-2502. Applies to Bell Models 212, 204B, and 205A-1 helicopters certificated in all categories. Compliance required as indicated after receipt of this AD. Prior to next flight, remove the main rotor blades having the following Serial Numbers: A2-28211, A2-29920, A2-29325, A2-28198, A2-27872, A2-28195, A2-29315, A2-29919, A2- 29334, A2-29915, A2-28016, A2-27961, A2-27982, A2-27963, A2-28023, A2-28015, A2-28019, A2-27968, A2-27967, A2-28020, A2-03642, A2-03646, and A2-03643. This supersedes airmail letter dated December 24, 1975, and Amendment 39-2488 (41 F.R. 1738), AD 76-01-05. This amendment is effective February 1, 1976, and was effective upon receipt for all recipients of the letter dated January 8, 1976, which contained this amendment.
2012-05-06: We are superseding an existing airworthiness directive (AD) for all Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 airplanes. That AD currently requires implementation of a Supplemental Inspection Document (SID) program of structural inspections to detect fatigue cracking, and repair if necessary, to ensure continued airworthiness of these airplanes as they approach the manufacturer's original fatigue design life goal. This new AD adds Model L-1011-385-3 airplanes to the applicability, changes certain inspection thresholds, adds three new structurally significant details (SSDs), and removes an SSD that has been addressed by a different AD. This AD was prompted by an evaluation by the manufacturer of usage and flight data that provided additional information about certain SSDs where fatigue damage is likely to occur. We are issuing this AD to prevent fatigue cracking that could compromise the structural integrity of these airplanes.
75-01-07: 75-01-07 BEECH: Amendment 39-2065. Applies to Beech Models S35, V35, V35A and V35B airplanes certificated in all categories with Continental TS1O-520-D engines installed in accordance with STC SA1035WE or Beech Drawing No. 35-910028. Compliance required as indicated, unless previously accomplished. To minimize exhaust system failures, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this airworthiness directive, conduct a visual inspection of the bellows portion of the exhaust wastegate elbow assembly, AiResearch Part Number 286-S35-074-137. If a crack is found, the elbow assembly must be modified per paragraph (b) below prior to further flight. (b) Within the next 100 hours time in service after the effective date of this airworthiness directive, but not later than July 1, 1975, remove the exhaust wastegate elbow assembly, AiResearch Part Number 286-S35-074-137 and cut off the bellows portion in accordance withAiResearch Aviation Company Service Bulletin No. 14.1.12 dated December 24, 1974 or later FAA approved revision thereto. Reinstall the elbow using adapter sleeve, AiResearch Part Number 286-S35-074-141. Equivalent modification may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: For the requirements regarding the listing of compliance of and method of compliance with this airworthiness directive in the permanent record of the airplane, see FAR 91- 173. This amendment becomes effective January 13, 1975.